CN113358210B - Pressure pulsation-based supercharger turbine blade vibration monitoring method - Google Patents
Pressure pulsation-based supercharger turbine blade vibration monitoring method Download PDFInfo
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- CN113358210B CN113358210B CN202110586307.4A CN202110586307A CN113358210B CN 113358210 B CN113358210 B CN 113358210B CN 202110586307 A CN202110586307 A CN 202110586307A CN 113358210 B CN113358210 B CN 113358210B
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- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- G—PHYSICS
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- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses a method for monitoring vibration of a turbine blade of a supercharger based on pressure pulsation, which comprises the following steps: detecting pressure information, pulse signals and rotating speed information of the turbine blade by adopting a sensor unit; acquiring the maximum natural frequency and the minimum natural frequency of the blade at normal temperature; obtaining corresponding natural frequency under the thermal state operation condition, and predicting the range of the turbine blade resonance rotating speed; controlling the turbine to operate in a relevant blade resonance mode, and obtaining the natural frequency of the blade by adopting a method of traversing the resonance rotating speed of the turbine: the method comprises the steps of selecting a section of turbine blade resonance rotating speed range containing actual resonance frequency multiplication of blades, synchronously acquiring pressure, rotating speed and phase discrimination signals under the condition that the turbine blades run at an increased speed or a decreased speed, and subdividing the signals with the filtered blade vibration natural frequency according to each rotation circle of the turbine by combining pulse signals generated by the phase discrimination sensor to enable the signals to correspond to the turbine blades one by one, so that the turbine blades with the maximum blade vibration are determined.
Description
Technical Field
The invention relates to the technical field of online detection of vibration of turbine blades of an exhaust gas turbocharger, in particular to a method for monitoring vibration of turbine blades of a turbocharger based on pressure pulsation.
Background
The exhaust gas turbocharger drives a turbine to rotate at a high speed by using high-temperature, high-pressure and high-speed exhaust gas discharged by an engine, so as to drive a coaxial compressor impeller to suck and compress a large amount of fresh air and send the fresh air into an engine cylinder. Exhaust gas turbochargers are used not only to reduce the size of the engine for the same power output, but also to greatly improve the engine's power performance, fuel economy and reduce emissions.
Turbines are usually designed with identical blades, which ideally should be the case. However, in reality, the material properties (primarily young's modulus) and geometry of actual turbine blades vary, resulting in blades having different natural frequencies (detuning) from blade to blade. Turbine blade detuning has a large effect on the high cycle fatigue life of the blade: it causes the vibration energy to be concentrated on one or several individual blades, thereby greatly amplifying the vibration amplitude of these blades well above the ideal, tuned state. Therefore, in evaluating the high cycle fatigue life of the turbine, it is necessary to find the blade with the highest risk, that is, the blade with the highest vibration strain.
The vibrational strain of the turbine blade can be measured by a variety of methods. Such as strain gage measurements, tip timing, etc. Strain gage measurement is one method of making strain measurements on turbine blades to measure blade deformation during operation of the turbine. This method has the following disadvantages: because the size of the turbine blade of the supercharger is small, the damping of the blade is greatly increased by sticking a strain gauge on the blade and adding a high-temperature protective layer, and the measured strain is different from the real strain; the turbine with small size has a thin shaft, and leads of all strain gauges are difficult to be led out from a central hole of the shaft, so that all turbine blades cannot be measured simultaneously, and multiple tests are required; making the test time consuming and expensive. The tip timing method used in the aviation industry also began to be applied to turbine blade vibration testing, and the method has the advantages that the turbine is in an actual working state, and the vibration of all blades can be measured at the same time. The disadvantages are that the testing and signal processing is complex and time consuming and that the testing equipment is expensive. Before testing, which blade has the largest vibration strain generated due to the detuning effect is determined by a simple method, and then strain gauge measurement is applied in a targeted mode.
Disclosure of Invention
According to the problems in the prior art, the invention discloses a method for monitoring vibration of a turbine blade of a supercharger based on pressure pulsation, which specifically comprises the following steps:
detecting pressure information, phase discrimination signals and rotating speed information of the turbine blade by adopting a sensor unit;
controlling the turbine to operate in a relevant blade resonance mode, and measuring a turbine blade pressure pulsation signal;
obtaining the natural frequency of the turbine blade at normal temperature, recording the frequency of each blade, and collecting the maximum natural frequency f of the blade at normal temperature max-cold And a small natural frequency f min-cold ；
The influence of the temperature softening effect and the centrifugal strengthening effect on the natural frequency of the blade and the shift phenomenon of the resonance point frequency caused by the fact that the turbine speed rises or falls through the resonance point of the blade are considered, so that the corresponding natural frequency f under the thermal state operation condition is obtained min-hot 、f max-hot ；
Estimating the synchronous vibration frequency multiplication N which may occur to the measured blade according to the actual measured rotating mechanical property, searching a pre-scanned turbocharger rotating speed range by adopting a Campbell diagram, and drawing two calculation frequencies on the Campbell diagram so as to estimate the turbine blade resonance rotating speed range;
Nmin in rpm＝60/N*f min-hot
Nmax in rpm＝60/N*f max-hot
the natural frequency of the blade is obtained by adopting a traversing turbine resonance rotating speed method: selecting a section of turbine blade resonance rotating speed range containing actual resonance frequency multiplication of the blade, synchronously acquiring pressure, rotating speed and phase discrimination signals under the condition of turbine blade acceleration or deceleration operation, and carrying out frequency f min-hot ～f max-hot And the signals of the natural frequency of the blade vibration filtered out are subdivided according to each rotation of the turbine so as to correspond to the turbine blades one by one, thereby determining the turbine blades with the maximum blade vibration.
Further, the sensor unit is including setting up pressure sensor, phase discrimination synchronous sensor and the speed sensor on the volute, pressure sensor is used for detecting the pressure signal that can provide turbine blade vibration information, phase discrimination synchronous sensor is used for detecting the phase discrimination signal that can provide turbine blade phase information, speed sensor is used for detecting the rotational speed information of turbine, thereby the sensor unit is through carrying out the analysis to pressure signal and extracting the vibration information of all blades when passing through synchronous resonance revolution speed zone.
Further, a natural frequency signal of the turbine blade vibration is obtained by a band-pass filtering method based on the pressure signal acquired by the pressure sensor, and the natural frequency of the turbine blade abnormal vibration is identified.
Further, the turbine blades are either ramped up or down for swept frequency excitation that traverses the turbine resonant rotational speed, where traversing the turbine resonant rotational speed is the frequency multiplication N for the selected excitation vibration, sweeping the turbocharger rotational speed range from Nmin rpm to Nmax rpm, thereby performing a resonance test on the turbine blades.
Furthermore, zero-phase band-pass filtering is carried out by taking the estimated inherent frequency bandwidth of the turbine blade as a passband, signals of the inherent frequency of blade vibration are filtered out without phase difference, and pulse signals generated by a phase discrimination sensor are combined to determine the turbine blade with the maximum blade vibration.
Since the vibration of the turbine blades produces pressure fluctuations that are proportional to the amplitude of the vibration when these signals are received by a nearby sensitive pressure sensor, which resonates with a particular frequency, dynamic pressure sensors can be used to detect pressure waves associated with blade vibration. According to the method for monitoring the vibration of the turbine blade of the supercharger based on the pressure pulsation, provided by the invention, the abnormal vibration of a single blade or a plurality of blades can be monitored and identified, and the blade being measured can be known in real time by synchronizing the phase discrimination sensor signal and the pressure signal, so that the measurement result of the method has the effects of accuracy, reliability, economy and quickness.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a flow chart of a synchronization detection method of the present invention;
FIG. 2 is a time domain signal graph of the natural frequency of blade vibration filtered out in an embodiment of the present invention;
FIG. 3 is a graph of a spectrum of a maximum amplitude of vibration of an associated turbine blade in accordance with an embodiment of the present invention;
FIG. 4 is an enlarged view of the spectrum of an embodiment of the present invention;
FIG. 5 is a diagram of a segment of FIG. 2 with a larger amplitude signal according to an embodiment of the present invention;
fig. 6 is a diagram of pulse signals detected by the synchronous phase detection sensor corresponding to the time period of fig. 5 in an embodiment of the present invention;
fig. 7 is a graph comparing the filtered signal of fig. 5 with the phase detected signal of fig. 6 in an embodiment of the present invention.
Detailed Description
In order to make the technical solutions and advantages of the present invention clearer, the following describes the technical solutions in the embodiments of the present invention clearly and completely with reference to the drawings in the embodiments of the present invention:
as shown in fig. 1, a method for monitoring vibration of a turbine blade of a supercharger based on pressure pulsation specifically includes the following steps:
s1: the pressure information, pulse signals and rotating speed information of the turbine blade are detected by adopting a sensor unit, a detection scheme of a dynamic pressure sensor is firstly determined, and in the figure 1, a high-temperature and high-sensitivity pressure sensor is installed on a volute.
The turbine blade vibration detection device comprises a sensor unit, a turbine blade vibration detection unit and a turbine blade vibration detection unit, wherein the sensor unit comprises a pressure sensor, a phase discrimination synchronous sensor and a rotating speed sensor which are arranged on a volute, the pressure sensor is used for detecting pressure signals capable of providing turbine blade vibration information, the phase discrimination synchronous sensor is used for detecting phase discrimination signals capable of providing turbine blade phase information, the rotating speed sensor is used for detecting rotating speed information of a turbine, and the sensor unit analyzes the pressure signals to extract vibration information of all blades when passing through a synchronous resonance rotating speed region.
S2: the measurement of the pressure pulsation signal of the turbine blade is carried out, and in order to excite the blade, the turbine must operate under the resonance condition of the vibration mode of the relevant blade, and the specific steps are as follows:
s21: experimentally obtaining the natural frequency of the turbine blade at room temperature by a knock test or other method, recording the frequency of each blade, and then giving the maximum and minimum natural frequencies f of the blade at room temperature max-cold And f min-cold ；
S22: the temperature softening effect, the centrifugal strengthening effect and the influence of the change rate of the turbine speed on the natural frequency of the blade need to be considered so as to obtain the corresponding frequency under the thermal state operation condition; for example, for a turbine of K418 material,obtaining blade frequency f under the conditions of inlet total temperature of about 600 ℃ and turbine speed change rate of +3/1000 per second max-cold And f min-cold 3% are subtracted in each case in order to make possible a correction, i.e. to calculate the corresponding natural frequency under hot operating conditions, using the following formula:
f max-hot ＝0.97*f max-cold
f min-hot ＝0.97*f min-cold
s23: and (4) estimating the synchronous vibration frequency multiplication NR (noise) possibly generated by the measured blade according to the actual measured rotating mechanical property, and searching the rotating speed range of the turbocharger to be scanned by using a Campbell diagram. Two calculated frequencies are plotted on a campbell plot to determine the range of possible resonant turbine speeds.
Nmin in rpm＝60/N*f min-hot
Nmax in rpm＝60/N*f max-hot
S24: and parameters such as natural frequency of the blade are accurately obtained by adopting a traversing turbine resonance rotating speed method.
In fig. 1, the turbocharger rotor blade is controlled to run at a relatively constant small acceleration speed increase or decrease, a section of turbine blade resonance rotating speed range containing the actual resonance frequency multiplication of the blade is selected, pressure, rotating speed and phase discrimination signals are synchronously acquired under the condition of turbine blade speed increase or decrease, and then the frequency f is used for detecting the turbine blade resonance rotating speed range min-hot ～f max-hot Zero-phase band-pass filtering is carried out on a passband, and signals of the natural frequency of the blade vibration are filtered out without phase difference; and dividing the signal of filtering out the natural frequency of the blade vibration according to each rotation of the turbine by combining pulse signals generated by the phase discrimination sensor, so that the signal corresponds to the turbine blades one by one, and determining the turbine blades with the maximum blade vibration.
The following is an embodiment of a method for detecting synchronous vibration parameters of high-speed rotating blades at variable speed.
S1: determining a detection scheme of a dynamic pressure sensor, and mounting a high-temperature and high-sensitivity pressure sensor on a volute; the method comprises the steps that cutting processing is carried out on the tip of a certain long blade of a turbocharger compressor and serves as a phase calibration point of a circumferential position of each circle of rotation of the turbocharger, the position of the long blade of the turbocharger compressor subjected to cutting processing corresponds to the tip of a No. 2 turbine blade in the axial direction of a rotor, and in the process of each circle of rotation of the rotor, a long square-wave-shaped electric pulse signal is output by a phase discrimination sensor at the tip of the long blade of the turbocharger compressor subjected to cutting processing.
S2: the measurement of the pressure pulsation signal of the turbine blade is carried out, and in order to excite the blade, the turbine must operate under the resonance condition of the vibration mode of the relevant blade, and the specific steps are as follows:
s21: the natural frequencies of the bending modes of the first-stage blades of a certain type of turbocharger turbine blade measured at room temperature are shown in table 1, the frequency of each blade is recorded, and then the maximum and minimum natural frequencies f of the blade at normal temperature are given max-cold ＝8640Hz，f min-cold ＝9740Hz；
S22: the temperature softening effect, the centrifugal strengthening effect and the influence of the change rate of the turbine speed on the natural frequency of the blade need to be considered so as to obtain the corresponding frequency under the thermal state operation condition; for example, for a K418 material turbine, at around 600 ℃ inlet total temperature and a turbine speed rate of change of +3/1000 per second, the blade frequency f is obtained max-cold And f min-cold Each minus 3% in order to make possible a correction, i.e. to calculate the corresponding natural frequency under hot operating conditions using the following formula:
f max-hot ＝0.97*f max-cold ＝9448Hz
f min-hot ＝0.97*f min-cold ＝8380Hz
s23: and (4) estimating the possible synchronous vibration frequency multiplication N =5 of the tested blade according to the actual performance of the tested turbocharger, and searching the rotating speed range of the turbocharger to be scanned by using a Campbell diagram. The two calculated frequencies are plotted on a campbell diagram, thereby determining the resonant speed range of the 5 th order multiple excitation of the turbine,
Nmin in rpm＝60/N*f min-hot ＝100560rpm
Nmax in rpm＝60/N*f max-hot ＝113376rpm
s24: and parameters such as natural frequency of the blade are accurately obtained by adopting a traversing turbine resonance rotating speed method.
The rotation speed of a rotor of the turbocharger is controlled to start from 100000rpm, the turbocharger is operated at a rotation speed increasing speed of about 300rpm per second until 114000rpm, and pressure, rotation speed and phase discrimination signals are synchronously acquired. Processing the pressure signals in sections one by one, carrying out zero-phase band-pass filtering by taking the frequency 8380-9450 Hz as a passband, and filtering out signals of the natural frequency of the blade vibration without phase difference; then, performing spectrum analysis on the filtered signals, wherein the characteristic frequency with the largest amplitude is that the relevant blades of the turbine operate under the condition of a resonance mode, fig. 3 shows the frequency spectrum with the largest vibration amplitude of the relevant turbine blades, fig. 4 shows an enlarged view of the signal frequency spectrum, the blade frequency with the largest vibration amplitude is 8882Hz, and fig. 2 shows the corresponding time domain signals of the natural vibration frequency of the filtered blades; in fig. 2, a section of signal with a large amplitude is intercepted, as shown in fig. 5, and then, in combination with the pulse signal detected by the synchronous phase detection sensor of fig. 6, the signal of filtering out the natural frequency of blade vibration of fig. 5 is subdivided according to each rotation of the turbine, so that the signal corresponds to the turbine blades one by one, as shown in fig. 7, the turbine blade with the largest blade vibration amplitude can be determined to be the blade 2.
In conjunction with the natural frequency of 9100Hz for turbine blade 2, measured at room temperature in Table 1, it was determined that the blade frequency was approximately 8882Hz for the turbine thermal operating condition identified by the present method as having the greatest blade vibration.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (5)
1. A method for monitoring vibration of a turbine blade of a supercharger based on pressure pulsation is characterized by comprising the following steps:
detecting pressure information, phase discrimination signals and rotating speed information of the turbine blade by adopting a sensor unit;
controlling the turbine to operate in a relevant blade resonance mode, and measuring a turbine blade pressure pulsation signal;
collecting natural frequency of turbine blade at normal temperature, recording frequency of each blade, and obtaining maximum natural frequency f of blade at normal temperature max-cold And minimum natural frequency f min-cold ；
The influence of the temperature softening effect and the centrifugal strengthening effect on the natural frequency of the blade and the resonance point frequency shift phenomenon caused by the fact that the turbine speeds up or down pass through the resonance point of the blade are considered, so that the corresponding minimum natural frequency f under the thermal state operation condition is obtained min-hot And maximum natural frequency f max-hot ；
Estimating the synchronous vibration frequency multiplication N possibly generated by the measured blade according to the actual measured rotating mechanical performance, searching the pre-scanned rotating speed range of the turbocharger by adopting a Campbell diagram, and converting the minimum natural frequency f min-hot And maximum natural frequency f max-hot The method is drawn on a Campbell diagram, so that the resonance rotating speed range of the turbine blade is estimated;
Nmin in rpm＝60/N×f min-hot
Nmax in rpm＝60/N×f max-hot
the natural frequency of the blade is obtained by adopting a traversing turbine resonance rotating speed method: selecting a section of turbine blade resonance rotating speed range containing actual resonance frequency multiplication of the blades, synchronously acquiring pressure, rotating speed and phase discrimination signals under the condition of turbine blade speed increasing or decreasing operation, and performing frequency f min-hot ～f max-hot The method comprises the steps of carrying out zero-phase band-pass filtering on a pressure signal for a passband, filtering and outputting a signal of the natural frequency of blade vibration without phase difference, and subdividing the signal of the natural frequency of the blade vibration filtered out according to each rotation of a turbine by combining pulse signals generated by a phase discrimination sensor to enable the signal to correspond to the turbine blades one by one, so that the turbine blades with the largest blade vibration are determined.
2. The method of claim 1, wherein: the sensor unit includes pressure sensor, phase discrimination sensor and speed sensor, pressure sensor is used for detecting the pressure signal that can provide turbine blade vibration information, phase discrimination sensor is used for detecting the phase discrimination signal that can provide turbine blade phase information, speed sensor is used for detecting the rotational speed information of turbine, thereby the sensor unit is through carrying out the analysis to pressure signal and drawing the vibration information that all blades pass through resonance rotational speed scope.
3. The method of claim 1, wherein: and obtaining a turbine blade vibration natural frequency signal by adopting a band-pass filtering method based on the pressure signal acquired by the pressure sensor, and identifying the natural frequency of the abnormal vibration of the turbine blade.
4. The method of claim 1, wherein: and performing frequency sweep excitation of traversing turbine resonant rotating speed by the turbine blade speed increasing or reducing, wherein the traversing turbine resonant rotating speed is the rotating speed range of the turbocharger from Nmin in rpm to Nmax in rpm for the selected synchronous vibration frequency doubling N, so as to perform resonance test on the turbine blade.
5. The method of claim 3, wherein: and performing zero-phase band-pass filtering by taking the pre-estimated inherent frequency bandwidth of the turbine blade as a passband, filtering out signals of the inherent frequency of the blade vibration without phase difference, and determining the turbine blade with the maximum blade vibration by combining pulse signals generated by a phase discrimination sensor.
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